EP2781560A1 - Système de revêtement de liaison et composant revêtu - Google Patents

Système de revêtement de liaison et composant revêtu Download PDF

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Publication number
EP2781560A1
EP2781560A1 EP20140159098 EP14159098A EP2781560A1 EP 2781560 A1 EP2781560 A1 EP 2781560A1 EP 20140159098 EP20140159098 EP 20140159098 EP 14159098 A EP14159098 A EP 14159098A EP 2781560 A1 EP2781560 A1 EP 2781560A1
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European Patent Office
Prior art keywords
percent
alloy
coating layer
nickel
cobalt
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EP20140159098
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German (de)
English (en)
Inventor
Surinder Singh Pabla
Kivilcim ONAL
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General Electric Co
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General Electric Co
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    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D1/00—Coating compositions, e.g. paints, varnishes or lacquers, based on inorganic substances

Definitions

  • the subject matter disclosed herein relates to metallic alloy compositions suitable for use in high temperature environments, and more particularly to metallic alloy compositions suitable for use as bond coat materials in high temperature environments to provide protection from oxidation.
  • metallic overlay or bond coatings i.e. MCrAlY and/or aluminides
  • thermal barrier coatings TBCs
  • the TBC provides a heat-reducing barrier between the hot combustion gases and the metal alloy substrate, and can prevent, mitigate, or reduce potential heat and corrosion induced damage to the substrate.
  • MCrAlY alloys are a family of high temperature coatings, wherein M is selected from one or a combination of iron, nickel and cobalt; and Cr is chromium, Al is aluminum, and Y is yttrium. These include MCrAlY coatings with gamma and beta phases in the alloy microstructures.
  • Various alloying elements, such as Si, Hf, Pd and Pt, have been added to gamma/beta MCrAlY alloys to improve oxidation resistance, but this may lead to reduction in strain tolerance of the bond coat materials and may also result in reduction of spallation life of the coating systems in which they have been employed, particularly those which include TBCs.
  • a bond coating system in an exemplary embodiment, includes a bond coat including a first coating layer adjacent a substrate and a second coating layer adjacent the first coating layer and a top coat.
  • the first coating layer includes a ⁇ / ⁇ microstructure.
  • the second coating layer includes a ⁇ / ⁇ '+ ⁇ microstructure.
  • a coated component in another exemplary embodiment, includes a substrate having a surface, a first coating layer disposed on the surface, the first coating including a ⁇ / ⁇ microstructure, and a second coating layer disposed on the first coating layer, the second coating layer including a ⁇ / ⁇ '+ ⁇ microstructure.
  • an exemplary bond coat system and coated component Provided is an exemplary bond coat system and coated component.
  • One advantage of the present disclosure is a bond coating system more capable of resisting oxidation.
  • Another advantage of an embodiment of the present disclosure is a longer spall life provided in a cost effective way.
  • GTD-111 has a nominal composition, in weight percent of the alloy, of 14 percent chromium, 9.5 percent cobalt, 3.8 percent tungsten, 1.5 percent molybdenum, 4.9 percent titanium, 3.0 percent aluminum, 0.1 percent carbon, 0.01 percent boron, 2.8 percent tantalum, and the balance nickel and incidental impurities.
  • Rene N4 has a nominal composition, in weight percent of the alloy, of 7.5 percent cobalt, 9.75 percent chromium, 4.20 percent aluminum, 3.5 percent titanium, 1.5 percent molybdenum, 4.8 percent tantalum, 6.0 percent tungsten, 0.5 percent columbium (niobium), 0.05 percent carbon, 0.15 percent hafnium, 0.004 percent boron, and the balance nickel and incidental impurities.
  • Rene 108 has a nominal composition of 0.07-0.10 percent carbon, 8.0-8.7 percent chromium, 9.0-10.0 percent cobalt, 0.4-0.6 percent molybdenum, 9.3-9.7 percent tungsten, 2.5-3.3 percent tantalum, 0.6-0.9 percent titanium, 5.25-5.75 percent aluminum, 0.01-0.02 percent boron, 1.3-1.7 percent hafnium, 0.1 percent maximum manganese, 0.06 percent maximum silicon, 0.01 percent maximum phosphorus, 0.004 percent maximum sulfur, 0.005-0.02 percent zirconium, 0.1 percent maximum niobium, 0.1 percent maximum vanadium, 0.1 percent maximum copper, 0.2 percent maximum iron, 0.003 percent maximum magnesium, 0.002 percent maximum oxygen, 0.002 percent maximum nitrogen, balance nickel and incidental impurities.
  • the bond coating system 210 includes a first coating layer 212 and a second coating layer 214.
  • First coating layer 212 includes a first MCrAlX alloy 260.
  • Second coating layer 214 includes a second MCrAlX alloy 270.
  • Bond coating system 210 is used to coat various high temperature articles, particularly various components 20 of a turbine engine 10, and even more particularly for use as a bond coating system 210 for various components 20 of an industrial gas turbine that comprise the hot gas flow path 18 and surfaces 30 that are exposed to the high temperature combustion gases that flow through this path.
  • Bond coating system 210 is particularly well-suited for use with various turbine blades (or turbine buckets) 50, but is also well suited for use with other components, including vanes (or turbine nozzles) 52, shrouds 54, combustors 58, fuel nozzles 60, transition pieces, combustor liners and the like, and including subcomponents and subassemblies of these components.
  • a combustor 58 generally comprises an assembly of a plurality of components, including various subassemblies, and bond coat system 210 may be incorporated on any or all of the components and subassemblies.
  • Bond coating system 210 may be applied to any suitable substrate 200, particularly various superalloy substrates 200, including Co-based, Ni-based or Fe-based superalloy substrates, or combinations thereof.
  • bond coating system 210 disclosed herein may be used, for example, on the pressure or suction surface of the airfoil section or blade tip of a gas turbine blade 50, as illustrated in FIG. 1 .
  • a surface 30 of a component 20, such as turbine blade 50 is protected by bond coating system 210 as a metallic protective coating layer, as illustrated in greater detail in FIG. 2 , which depicts an enlargement of a section through the surface 30 of a component 20, such as a turbine blade 50.
  • Surface 30 may include any portion of the component 20 on which it is desirable to provide bond coating system 210 to protect substrate 200 from oxidation, including surfaces 30 that comprise hot gas flow path 18 and are directly exposed to the hot combustion gases that flow through this path, as well as other surfaces, including those that are not directly exposed to the hot combustion gases, but which may be exposed to high temperatures resulting from these gases.
  • surface 30 may include the surface of the airfoil section or blade tip of turbine blade 50.
  • Bond coating system 210 may be used by itself to protect surface 30, as shown in FIG. 6 , or may be used in conjunction with other high temperature materials, including other high temperature coating materials, to provide a protective system 230 of coating layers, as described herein, wherein bond coating system 210 may be used, for example, as an under layer or an inner layer or an outer layer, or a combination thereof, in such a system.
  • Protective system 230 may include bond coating system 210 as an under layer as part of a combination of coating layers that also includes one or more thermal barrier coating (TBC) layer 240, or one or more aluminide coating layer 250, or one or more other bond coat layers, or a combination thereof.
  • protective system 230 may include bond coating system 210 as an oxidation resistant under layer for at least one TBC layer 240, wherein bond coating system 210 is disposed on surface 30 of substrate 200, such as a superalloy substrate, and at least one TBC layer 240 is disposed on bond coating system 210 and may be subject to exposure to the hot combustion gas.
  • protective system 230 may include bond coating system 210 as an oxidation resistant under layer for at least one aluminide layer 250, wherein the bond coating system 210 is disposed on surface 30 of substrate 200, such as a superalloy substrate, and at least one aluminide layer 250 is disposed on bond coating system 210 and may be subject to exposure to the hot combustion gas.
  • protective system 230 may include bond coating system 210 as an oxidation resistant under layer for aluminide layer 250 and TBC layer 240, wherein bond coating system 210 is disposed on surface 30 of substrate 200, at least one aluminide layer 250 is disposed on bond coating system 210 and at least one TBC layer 240 is disposed on aluminide layer 250 and may be subject to exposure to the hot combustion gas.
  • Protective system 230 may also include bond coating system 210 as an inner layer as part of a combination of coating layers that also includes one or more thermal barrier coating (TBC) layer 240, or one or more aluminide layer 250, or a combination thereof.
  • TBC thermal barrier coating
  • protective systems 230 of FIGS. 2-4 may optionally include at least one aluminide layer 250 or another bond coat layer disposed on substrate 200, between substrate 200 and bond coating system 210. Otherwise, the arrangement of bond coating system 210 layer, aluminide layer 250 and TBC layer 240 is as described above in FIGS. 2-4 .
  • protective system 230 may include bond coating system 210 as an outer layer as part of a combination of coating layers that also includes one or more thermal barrier coating (TBC) layer 240, or one or more aluminide layer 250, or a combination thereof.
  • TBC thermal barrier coating
  • Other combinations of one or more bond coating system 210 layers as an outer layer, in combination with one or more TBC layer 240 or one or more aluminide layer 250, or another bond coat layer, or a combination thereof, are also possible.
  • protective system 230 may include just bond coating system 210 as an outer layer, not in combination with other coating layers.
  • First coating layer 212 includes a ⁇ / ⁇ microstructure.
  • Second coating layer 214 includes a ⁇ / ⁇ '+ ⁇ microstructure.
  • first coating layer 212 has a thickness of about 25.4 microns (1 milli-inch) to about 1524 (60 milli-inches) or alternatively about 76 microns (3 milli-inches) to about 1270 microns (50 milli-inches) or alternatively about 178 microns (7 milli-inches) to about 1143 microns (45 milli-inches).
  • second coating layer 214 has a thickness of about 25.4 microns (1 milli-inch) to about 762 microns (30 milli-inches) or alternatively about 76 microns (3 milli-inches) to about 635 microns (25 milli-inches) or alternatively about 178 microns (7 milli-inches) to about 508 microns (20 milli-inches).
  • first coating layer 212 includes a first alloy 260 and second coating layer 214 includes second alloy 270.
  • First alloy 260 and second alloy 270 are generally superalloys that comprise cobalt, nickel or iron, or any combination thereof, including cobalt-based, nickel-based or iron-based superalloys.
  • bond coating system 210 provides a good combination of high temperature oxidation resistance, TBC spallation resistance and ductility.
  • a metal-based e.g., cobalt, nickel or iron
  • the named metal e.g., cobalt-based
  • the metals are listed in descending order by weight of the alloy.
  • a cobalt-nickel-based alloy means that cobalt and nickel are the primary alloy constituents, by weight, with the weight fraction of cobalt being larger than that of nickel; and a nickel-cobalt-based alloy means that nickel and cobalt are the primary alloy constituents, by weight, with the weight fraction of nickel being larger than that of cobalt.
  • An example of an existing MCrAlY bond coat alloy used for turbine engine applications includes a conventional gamma-beta ( ⁇ / ⁇ ) MCrAlY (NiCrAlY) bond coat having a nominal composition, by weight of the alloy, 22 percent chromium, 10 percent aluminum, 1 percent yttrium, and the balance nickel and incidental impurities, where sulfur may be an incidental impurity, and is controlled to 100 parts per million (ppm) or less.
  • BC52 Another conventional gamma-gamma prime MCrAlY (NiCoCrAlY) bond coat known as BC52 has a nominal composition, by weight of the alloy, 18 percent chromium, 6.5 percent aluminum, 10 percent cobalt , 6 percent tantalum, 2 percent rhenium, 0.5 percent hafnium, 0.3 percent yttrium, 1.0 percent silicon, 0.015 percent zirconium, 0.06 percent carbon, 0.015 percent boron, and the balance nickel and incidental impurities.
  • Yet another example of an existing MCrAlY (NiCoCrAlY) bond coat alloy used for turbine engine application has a nominal composition, by weight of the alloy of about 25 percent to about 45 percent nickel, about 15 percent to about 30 percent chromium, about 8.0 percent to about 13 percent aluminum, about 0.19 percent to about 1.0 percent yttrium, and the balance cobalt and incidental impurities.
  • the cobalt-based, cobalt-nickel-based or nickel-cobalt-based superalloy first coating layer 212 bond coat 280 of bond coating system 210 includes a ⁇ / ⁇ microstructure.
  • First coating layer 212 includes a first MCrAlX alloy 260, where M includes cobalt, and may also optionally include nickel, and where X includes yttrium from about 0.001 percent to less than 0.19 percent by weight of the alloy and may also optionally include silicon or germanium, or a combination thereof.
  • First MCrAlX alloy 260 generally employs reduced amounts of yttrium compared to existing MCrAlY bond coat alloys used for turbine engine applications, which have a nominal composition that includes 0.3 percent Y, and where Y is known to range from 0.19 percent to 1.0 percent.
  • the reduced amounts of yttrium advantageously provide improved oxidation resistance and increased TBC spallation resistance for these alloys when used in protection systems 230 that also include TBC layer 240.
  • First MCrAlX alloy 260 may employ increased amounts of aluminum as compared to existing MCrAlY bond coat alloys, which advantageously further improves the oxidation resistance as compared to existing bond coat alloys.
  • First MCrAlX alloy 260 may also optionally employ germanium, which is not present in existing MCrAlY bond coat alloys, which also advantageously improves the ability to retain the beta phase for longer exposure times in turbine engine applications as described herein.
  • First MCrAlX alloy 260 may also optionally employ silicon, which advantageously improves oxidation resistance and TBC spallation life.
  • first MCrAlX alloy 260 is a cobalt-based, cobalt-nickel- based or nickel-cobalt-based MCrAlX alloy having a microstructure that includes gamma and beta phases wherein, by weight of the alloy, M comprises cobalt in an amount of at least about 27 percent and X comprises yttrium in an amount of about 0.001 percent to less than 0.19 percent by weight of the alloy. More particularly, yttrium may be present in an amount, by weight of the alloy, from about 0.001 percent to about 0.18 percent, alternatively from about 0.01 percent to about 0.18 percent, or alternatively from about 0.02 percent to about 0.15 percent.
  • First MCrAlX alloy 260 may also optionally include germanium in an amount, by weight of the alloy, from about 0.001 percent to about 1.5 percent, alternatively from about 0.01 percent to about 1.5 percent, or alternatively from about 0.2 percent to about 1.5 percent.
  • First MCrAlX alloy 260 may also optionally include silicon in an amount, by weight of the alloy, of up to about 1.5 percent, alternatively from about 0.01 percent to about 1.5 percent, or alternatively from about 0.1 percent to about 1.5 percent.
  • first MCrAlX alloy 260 may also be described as comprising a cobalt-nickel-based alloy, and may include, by weight of the alloy, from about 20.0 percent to about 82.0 percent nickel, from about 10.0 percent to about 28.0 percent chromium, from about 5.0 percent to about 15.0 percent aluminum, and yttrium and optionally germanium or silicon, or a combination thereof, in the amounts described above, including from about 0.001 percent to less than 0.19 percent yttrium, about 0.001 percent to about 1.5 percent germanium and up to about 1.5 percent silicon, and the balance cobalt and incidental impurities.
  • yttrium increases the resistance of first MCrAlX alloy 260 to oxidation and TBC spallation compared to, for example, existing bond coat alloys, and includes yttrium in a nominal amount of 0.3 percent.
  • Existing bond coat alloys are known to range in commercial practice from 0.19 percent to 1.0 percent by weight yttrium of the alloy, and do not include germanium or silicon.
  • second coating layer 214 is a nickel-based superalloy bond coat material, and more particularly a nickel-cobalt-based superalloy bond coat material.
  • Second coating layer 214 includes a ⁇ / ⁇ '+ ⁇ microstructure.
  • Second coating layer 214 includes second MCrAlX alloy 270 wherein, by weight of second alloy, M comprises nickel in an amount of at least about 30.0 percent and X comprises from about 0.005 percent to about 0.19 percent yttrium.
  • Second MCrAlX alloy 270 generally employs reduced amounts of yttrium compared to existing MCrAlY bond coat alloys used for turbine engine applications, discussed above, such as, for example, BC52..
  • second MCrAlX alloy 270 disclosed herein advantageously provides improved oxidation resistance and increased TBC spallation resistance for these alloys when used in protective systems 230 that also include TBC layer 240.
  • second MCrAlX alloys 270 disclosed herein are silicon-free to prevent the possibility of formation of brittle TixSiy phases when used with alloys that include Ti and improve strain tolerance, have increased amounts of Al to improve oxidation resistance, and are rhenium-free to provide enhanced strain tolerance with regard to the onset of crack initiation and avoid the use of this strategically important element, which is strategic owing to its limited supply and associated cost.
  • Second MCrAlX alloy 270 also may employ germanium, which is not present in existing MCrAlY bond coat alloys, such as those described above.
  • second MCrAlX alloy 270 comprises a nickel-based MCrAlX alloy having a microstructure that includes gamma, beta and gamma prime phases wherein, by weight of the alloy, M comprises nickel in an amount of at least about 30 percent and X comprises from about 0.005 percent to about 0.19 percent yttrium.
  • second MCrAlX alloy 270 comprises a nickel-cobalt-based MCrAlX (NiCoCrAlX) alloy having a microstructure that includes gamma, beta and gamma prime phases wherein, by weight of the alloy, M comprises nickel in an amount of at least about 30 percent and cobalt in an amount of about 5.0 percent to about 15.0 percent, and X comprises yttrium in an amount from about 0.005 percent to about 0.19 percent. Second MCrAlX alloy 270 may also include germanium in an amount, by weight of the alloy, up to about 1.25 percent.
  • second MCrAlX alloy 270 comprises, by weight of the alloy, from about 5.0 percent to about 15.0 percent cobalt, from about 12.0 percent to about 28.0 percent chromium, from about 6.5 percent to about 11.0 percent aluminum, up to about 1.25 percent germanium, from about 4.0 percent to about 8.0 percent tantalum, from about 0.005 percent to about 0.05 percent zirconium, from about 0.005 percent to about 0.8 percent hafnium, from about 0.005 percent to about 0.19 percent yttrium, and the balance nickel and incidental impurities.
  • second MCrAlX alloy 270 comprises, by weight of the alloy, from about 8.5 percent to about 12.0 percent cobalt, from about 16.0 percent to about 21.0 percent chromium, from about 6.5 percent to about 8.5 percent aluminum, from about 4.5 percent to about 7 percent tantalum, from about 0.001 percent to about 0.1 percent zirconium, from about 0.1 percent to about 0.65 percent hafnium, from about 0.005 percent to about 0.19 percent yttrium, up to about 1.25 percent germanium, and the balance nickel and incidental impurities. Second MCrAlX alloy 270 has more aluminum than the existing gamma-gamma prime-beta bond coat alloys described herein.
  • Second MCrAlX alloys 270 described herein are substantially silicon-free and substantially rhenium-free (i.e., contain substantially no silicon or rhenium other than as an incidental impurity).
  • substantially silicon-free means that even where silicon may be present, such as by incorporation as an incidental impurity, it will comprise, by weight of the alloy, about 0.1 percent or less.
  • substantially rhenium-free means that even where Re may be present, such as by incorporation as an incidental impurity, it will comprise, by weight of the alloy, about 0.1 percent or less. Avoidance of the use of rhenium improves the strain tolerance and avoids the need for this strategic element.
  • yttrium and/or germanium increases the resistance of second MCrAlX alloy 270 to oxidation compared to, for example, existing bond coat alloys, as described herein, that include yttrium in a nominal amount of about 1 percent, and which do not include germanium.
  • First and second MCrAlX alloys 260 and 270 disclosed herein may be used in any suitable form, including as an alloy used to form an entire article of the types disclosed herein, or as a bond coating system 210.
  • First and second MCrAlX alloys 260 and 270 may be formed by any suitable method, including various vacuum melting methods, and particularly melting methods employed for various superalloys, particularly cobalt-based, cobalt-nickel-based, nickel-based or nickel-cobalt-based superalloys.
  • the bond coat material may be applied by vapor deposition, slurry deposition, or any thermal spray process including, but not limited to, high velocity oxygen fuel spraying (HVOF), high velocity air fuel spraying (HVAF), vacuum plasma spray (VPS), air plasma spray (APS), ion plasma deposition (IPD), electron-beam physical vapor deposition (EBPVD) and cold spray methods.
  • HVOF high velocity oxygen fuel spraying
  • HVAF high velocity air fuel spraying
  • VPS vacuum plasma spray
  • APS air plasma spray
  • IPD ion plasma deposition
  • EBPVD electron-beam physical vapor deposition
  • Protective system 230 may also include an aluminide layer 250 disposed relative to the bond coating system 210 material and other coatings, as described herein.
  • Aluminide layer 250 may include any suitable aluminide, including a diffusion aluminide, such as a simple diffusion aluminide or a complex diffusion aluminide, such as a platinum aluminide.
  • Aluminide layer 250 may have any suitable thickness, and in an exemplary embodiment, may have a thickness from about 12.7 microns (0.5 milli-inches) to about 101.6 microns (4 milli-inches) thick.
  • Protective system 130 may also include TBC layer 240 disposed relative to the bond coating system 210 material and other coatings, as described herein.
  • Any suitable thermal barrier layer 240 may be used, including a dense vertically microcracked (DVM) ceramic TBC layer 240.
  • TBC layer 140 may have any suitable thickness, and in an exemplary embodiment, may have a thickness from about 127 microns (5 milli-inches) to about 2032 microns (80 milli-inches).
  • first MCrAlX alloy 260 and second MCrAlX 270 increase the spallation resistance when applied to a superalloy substrate 200 as an under layer for a TBC layer 240 compared to a known bond coat 300.
  • the known bond coat 300 has a nominal composition, by weight of the alloy of about 30 percent to about 34 percent nickel, about 21 percent to about 24 percent chromium, about 9.5 percent to about 10.5 percent aluminum, about 0.1 percent to about 0.5 percent yttrium, and the balance cobalt and incidental impurities.
  • a known bond coating alloy 300 has a baseline number of hours to spallation.
  • First MCrAlX alloy 260 increases the spallation time compared to known bond coat 300 by more than 30 percent.
  • Second MCrAlX alloy 270 increases the spallation time compared to known bond coat 300 by more than 80 percent. Combining first MCrAlX alloy 260 and second MCrAlX 270 alloy to form bond coating system 210 should result in increased spallation resistance when bond coating system 210 is applied to a superalloy substrate 200.
  • the spallation resistance of protection system 230 comprising first MCrAlX alloy 260 and second MCrAlX alloys 270 as a bond coating system 210 material under a TBC layer 240 should have greater than the resistance of a protection system comprising known bond coat alloy 300 having higher amounts of yttrium under the same TBC layer 240.
  • first MCrAlX alloy 260 as first layer 214 and second MCrAlX alloy 270 as second layer 216 has the capability to enable the protection system 230 described, i.e., bond coating system 210/TBC coating layer 240, to achieve about the same spallation resistance at an average operating temperature that was about 1900°F or more higher than that of a protection system comprising the known bond coat alloy 300 and a TBC layer. Therefore, first MCrAlX alloy 260 and second MCrAlX alloy 270 should improve the spallation resistance sufficiently to enable longer operating lifetimes at the same operating temperature or the similar operating lifetimes at higher operating temperatures.
  • yttrium in the MCrAlX protective systems 230 disclosed herein improves oxidation resistance by delaying alumina spallation.
  • First MCrAlX alloy 260 and second MCrAlX alloy 270 were also tested by room temperature uniaxial tensile testing at a constant strain rate to assess their strain tolerance before crack initiation, as shown in FIG. 9 .

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  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Wood Science & Technology (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physical Vapour Deposition (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP20140159098 2013-03-18 2014-03-12 Système de revêtement de liaison et composant revêtu Withdrawn EP2781560A1 (fr)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3181727A1 (fr) * 2015-12-18 2017-06-21 General Electric Company Articles enrobés et procédé de fabrication
EP3470224A1 (fr) * 2017-10-10 2019-04-17 General Electric Company Article enrobé et procédé de fabrication
EP4361314A1 (fr) * 2022-10-24 2024-05-01 General Electric Company Système de revêtement pour composants nécessitant une réparation

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10202855B2 (en) 2016-06-02 2019-02-12 General Electric Company Airfoil with improved coating system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050031877A1 (en) * 2003-08-04 2005-02-10 Gigliotti Michael Francis X. Organic coating compositions for aluminizing metal substrates, and related methods and articles
US20110076410A1 (en) * 2009-09-30 2011-03-31 Andrew Jay Skoog Method for making strain tolerant corrosion protective coating compositions and coated articles

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050031877A1 (en) * 2003-08-04 2005-02-10 Gigliotti Michael Francis X. Organic coating compositions for aluminizing metal substrates, and related methods and articles
US20110076410A1 (en) * 2009-09-30 2011-03-31 Andrew Jay Skoog Method for making strain tolerant corrosion protective coating compositions and coated articles

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3181727A1 (fr) * 2015-12-18 2017-06-21 General Electric Company Articles enrobés et procédé de fabrication
CN107022758A (zh) * 2015-12-18 2017-08-08 通用电气公司 涂布制品和制造方法
US10017844B2 (en) 2015-12-18 2018-07-10 General Electric Company Coated articles and method for making
CN107022758B (zh) * 2015-12-18 2020-08-18 通用电气公司 涂布制品和制造方法
EP3470224A1 (fr) * 2017-10-10 2019-04-17 General Electric Company Article enrobé et procédé de fabrication
US10704133B2 (en) 2017-10-10 2020-07-07 General Electric Company Coated article and method for making
EP4361314A1 (fr) * 2022-10-24 2024-05-01 General Electric Company Système de revêtement pour composants nécessitant une réparation

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